Shock isolation system for spacecraft fairing

Abstract

A launch vehicle assembly has a launch vehicle body ( 10 ) having a first slot ( 48 a ) therein. A first magnet ( 50 a ) is disposed within the first slot ( 43 a ). A fairing assembly ( 12 ) is positioned adjacent to the vehicle body ( 10 ). The fairing assembly ( 12 ) has a second slot ( 30 a ) therein positioned opposite the first slot ( 48 a ). A second magnet ( 40 a ) is disposed within the second slot ( 30 a ) so that the second magnet ( 40 a ) repels the first magnet ( 50 a ).

What is claimed is:  
     
       1. A launch vehicle assembly comprising: 
       a launch vehicle body having a first slot therein;  
       a first magnet disposed within said first slot;  
       a fairing assembly positioned adjacent to the vehicle body, said fairing assembly having a second slot therein, said second slot positioned opposite said first slot;  
       a second magnet disposed within said second slot so that said second magnet repels said first magnet,  
       said fairing assembly contacting the launch vehicle body when a predetermined force acts on the payload fairing and levitating relative to the launch vehicle body when a force below the predetermined force acts on the fairing assembly.  
     
     
       2. A launch vehicle assembly as recited in  claim 1  wherein said first magnet and said second magnet comprise neodymium. 
     
     
       3. A launch vehicle assembly as recited in  claim 1  wherein said launch vehicle body comprises a payload attachment fitting, said first slot disposed within said payload attachment fitting. 
     
     
       4. A launch vehicle assembly as recited in  claim 1  wherein said first slot comprises a keyhole slot. 
     
     
       5. A launch vehicle assembly as recited in  claim 1  wherein said second slot comprises a keyhole slot. 
     
     
       6. A launch vehicle assembly comprising: 
       a launch vehicle body having a lip therearound, said lip having a first upper surface, a first lower surface and a first side surface extending between said first upper surface and said first lower surface, said first upper surface having a first slot therein, said first side surface having a second slot therein and said first lower surface having a third slot therein;  
       a first magnet disposed within said first slot;  
       a second magnet disposed within said second slot;  
       a third magnet disposed within said third slot;  
       a fairing assembly having a ring positioned adjacent to the lip, said ring having an second upper surface adjacent to said first upper surface, a second lower surface adjacent to said first lower surface and a second side surface adjacent to first side surface, said second upper surface having a fourth slot therein, said second side surface having a fifth slot therein and said second lower surface having a sixth slot therein;  
       a fourth magnet disposed within said fourth slot;  
       a fifth magnet disposed within said fifth slot;  
       a sixth magnet disposed within said sixth slot;  
       so that said first magnet repels said fourth magnet, said second magnet repels said fifth magnet and said third magnet repels said sixth magnet.  
     
     
       7. A launch vehicle assembly as recited in  claim 6  wherein said first magnet, said second magnet and said third magnet comprise neodymium. 
     
     
       8. A launch vehicle assembly as recited in  claim 6  wherein said fourth magnet, said fifth magnet, and said sixth magnet comprise neodymium. 
     
     
       9. A launch vehicle assembly as recited in  claim 6  wherein said launch vehicle body comprises a payload attachment fitting, said first slot disposed within said payload attachment fitting. 
     
     
       10. A launch vehicle assembly as recited in  claim 6  wherein said first slot, said second slot and said third slot comprise a keyhole slot. 
     
     
       11. A launch vehicle assembly as recited in  claim 6  wherein said fourth slot, said fifth slot and said sixth slot comprise a keyhole slot. 
     
     
       12. A method of operating a launch vehicle comprising; 
       positioning a payload fairing adjacent to a launch vehicle body;  
       contacting the payload fairing with the launch vehicle body above a predetermined force on the payload fairing;  
       levitating the payload fairing relative to the launch vehicle body below a predetermined force on the payload fairing; and  
       after levitating the payload fairing, releasing the payload fairing from the lunch vehicle.  
     
     
       13. A method as recited in  claim 12  wherein levitating comprises levitating the payload fairing relative to the launch vehicle body by magnetic repulsive force. 
     
     
       14. A method as recited in  claim 13  further comprising positioning a first magnet on the payload fairing and a second magnet on the payload fairing. 
     
     
       15. A method as recited in  claim 14  wherein positioning comprises positioning the first magnet in a first slot and a second magnet in a second slot. 
     
     
       16. A launch vehicle assembly comprising: 
       a launch vehicle body having a first slot disposed in a payload attachment fitting;  
       a first magnet disposed within said first slot, said first slot disposed within said payload attachment fitting;  
       a fairing assembly positioned adjacent to the vehicle body, said fairing assembly having a second slot therein, second slot positioned opposite said first slot;  
       a second magnet disposed within said second slot so that said second magnet repels said first magnet.